Thermal behavior of an isolator with mode transition inducing back-pressure of a dual-mode scramjet

作     者：Yang Qingchun Bao Wen Chetehouna Khaled Zhang Silong Gascoin Nicolas 

作者机构：School of Astronautics Beihang University 100083 China School of Energy Science and Engineering Harbin Institute of Technology 150001 Harbin China INSA Centre Val de Loir 88 Boulevard Lahitolle 18000 Bourges France 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2017年第30卷第2期

页      面：595-601页

核心收录：

学科分类：08[工学] 082502[工学-航空宇航推进理论与工程] 0802[工学-机械工程] 0825[工学-航空宇航科学与技术] 0801[工学-力学（可授工学、理学学位）] 

主　　题：Combustion mode Dual-mode scramjet Isolator Mode transition Thermal behavior 

摘      要：Combustion mode transition is a valuable and challenging research area in dual-mode scramjet engines.The thermal behavior of an isolator with mode transition inducing backpressure is investigated by direct-connect dual-mode scramjet experiments and theoretical analysis.Combustion experiments are conducted under the incoming airflow conditions of total temperature1270 K and Mach 2.A small increment of the fuel equivalence ratio is scheduled to trigger mode transition.Correspondingly,the variation of the coolant flow rate is very small.Based on the measured wall pressures,the heat-transfer model can quantify the thermal state variation of the engine with active cooling.Compared with the combustor,mode transition has a greater effect on the isolator thermal behavior,and it significantly changes the isolator heat-flux and wall temperature.To further study the isolator thermal behavior from flight Mach 4 to Mach 7,a theoretical analysis is carried out.Around the critical point of combustion mode transition,sudden changes of the isolator flowfield and thermal state are discussed.